DOT/FAA/AR-04/1 

Office of Aviation Research 

Washington, D.C. 20591

The Temperature Distribution 

Within Solid Metal Cylinders 

Subjected to a Standard Aircraft 

Engine Fire 

John W. Reinhardt 

Dung Do 

Jason Fayer 

April 2004 

Data Report 

This document is available to the U.S. public 

through the National Technical Information 

Service (NTIS), Springfield, Virginia 22161. 

U.S. Department of Transportation 

Federal Aviation Administration
NOTICE 

This document is disseminated under the sponsorship of the U.S. 

Department of Transportation in the interest of information exchange. The 

United States Government assumes no liability for the contents or use 

thereof. The United States Government does not endorse products or 

manufacturers. Trade or manufacturer's names appear herein solely 

because they are considered essential to the objective of this report. This 

document does not constitute FAA certification policy. Consult your local 

FAA aircraft certification office as to its use. 

This report is available at the Federal Aviation Administration William J. 

Hughes Technical Center’s Full-Text Technical Reports page: 

actlibrary.tc.faa.gov in Adobe Acrobat portable document format (PDF). 
Technical Report Documentation Page

1. Report No.

DOT/FAA/AR-04/1 

2. Government Accession No. 3. Recipient's Catalog No.

4. Title and Subtitle

THE TEMPERATURE DISTRIBUTION WITHIN SOLID METAL CYLINDERS 

5. Report Date

April 2004

SUBJECTED TO A STANDARD AIRCRAFT ENGINE FIRE 6. Performing Organization Code

7. Author(s)

John W. Reinhardt, Dung Do, and Jason Fayer 

8. Performing Organization Report No.

9. Performing Organization Name and Address

Federal Aviation Administration 

William J. Hughes Technical Center 

Airport and Aircraft Safety

10. Work Unit No. (TRAIS)

Research and Development Division 

Fire Safety Branch 

Atlantic City International Airport, NJ 08405 

11. Contract or Grant No.

12. Sponsoring Agency Name and Address

U.S. Department of Transportation 

Federal Aviation Administration

13. Type of Report and Period Covered

Data Report 

Office of Aviation Research 

Washington, DC 20591 

14. Sponsoring Agency Code

15. Supplementary Notes

16. Abstract

This report provides temperature data that could be used to establish the ultimate tensile strength (UTS) loss of candidate engine 

mount materials after been exposed to a standard flame for 5 and 15 minutes. The materials tested included 4130 steel

(baseline),15-5 PH steel, titanium 6A1-4V, Inconel 718, and aluminum 7075. These materials were instrumented internally 

with thermocouples and exposed to the standard flame. MIL-Handbook-5H provides some data with regards to the UTS loss of 

these materials while heated, but additional strength tests must be conducted to account for the higher temperatures experienced 

by these materials while exposed to the standard fire. 

17. Key Words

Engine mounts, Ultimate tensile strength loss, Fire 

18. Distribution Statement

This document is available to the public through the National

Technical Information Service (NTIS), Springfield, Virginia 

22161.

19. Security Classif. (of this report)

Unclassified 

20. Security Classif. (of this page)

Unclassified 

21. No. of Pages

38 

22. Price

Form DOT F1700.7 (8-72) Reproduction of completed page authorized 
TABLE OF CONTENTS 

Page 

EXECUTIVE SUMMARY vii 

1. INTRODUCTION 1 

2. TEST SPECIMENS, EQUIPMENT, AND INSTRUMENTATION 1 

2.1 Specimens 1 

2.2 Equipment 2 

2.2.1 Modified Oil Burner 2 

2.2.2 Specimen Fixture 2 

2.3 Instrumentation 2 

2.3.1 Data Acquisition System 3 

2.3.2 Thermocouples 3 

2.3.3 Calorimeter 3 

2.3.4 Dial Indicator and Index-Rotational Device 3 

3. PROCEDURES 3 

3.1 Calibration 3 

3.1.1 Temperature Calibration 4 

3.1.2 Heat Flux Calibration 4 

3.2 Burner Test 4 

4. RESULTS 4 

4.1 4130 Steel 5 

4.2 15-5 PH Steel 5 

4.3 Titanium 6A1-4V 5 

4.4 Aluminum 7075 5 

4.5 Inconel 718 6 

5. REFERENCES 6 

iii
LIST OF FIGURES

Figure Page 

1 Oil Burner 7 

2 Drawing of the Specimen Fixture 7 

3 Specimen Fixture 8 

4 Data Acquisition System 8 

5 Bar Thermocouples Insulation 9 

6 Thermocouple and Calorimeter Setup 10 

7 Relative Position Between Calorimeters, Calibration Thermocouples, and FireTesting Zone 11 

8 Calibration Calorimeters 11 

9 Fire Test of 4130 Steel Bar 12 

10 15-5 PH Steel Bar After Test 12 

11 Aluminum 7075 Bar After Test 13 

12 Time-Temperature Data During Test 1 of 4130 Steel 13 

13 Time-Temperature Data During Test 2 of 4130 Steel 14 

14 Time-Temperature Data During Test 3 of 4130 Steel 14 

15 Time-Temperature Data During Test 4 of 4130 Steel 15 

16 Time-Temperature Data During Test 5 of 4130 Steel 15 

17 Time-Temperature Data During Test 1 of 15-5 PH Steel 16 

18 Time-Temperature Data During Test 2 of 15-5 PH Steel 16 

19 Time-Temperature Data During Test 3 of 15-5 PH Steel 17 

20 Time-Temperature Data During Test 4 of 15-5 PH Steel 17 

21 Time-Temperature Data During Test 5 of 15-5 PH Steel 18 

22 Time-Temperature Data During Test 1 of Titanium 6A1-4V 18 

iv
23 Time-Temperature Data During Test 2 of Titanium 6A1-4V 19 

24 Time-Temperature Data During Test 3 of Titanium 6A1-4V 19 

25 Time-Temperature Data During Test 4 of Titanium 6A1-4V 20 

26 Time-Temperature Data During Test 5 of Titanium 6A1-4V 20 

27 Time-Temperature Data During Test 1 of Aluminum 7075 21 

28 Time-Temperature Data During Test 2 of Aluminum 7075 21 

29 Time-Temperature Data During Test 3 of Aluminum 7075 22 

30 Time-Temperature Data During Test 4 of Aluminum 7075 22 

31 Time-Temperature Data During Test 5 of Aluminum 7075 23 

32 Time-Temperature Data During Test 1 of Inconel 718 23 

33 Time-Temperature Data During Test 2 of Inconel 718 24 

34 Time-Temperature Data During Test 3 of Inconel 718 24 

35 Time-Temperature Data During Test 4 of Inconel 718 25 

36 Test Fixture During the Determination of the Specimen Maximum Deflection 25 

37 Test Fixture During the Determination of the Specimen Maximum Deflection 

Angular Location 26 

38 Specimen Maximum Deflection Location 27 

LIST OF TABLES 

Table Page 

1 Test Specimen Description 28 

2 Summary of Results 29 

3 Comparison Between Test Data and MIL-Handbook-5H 30 

4 Material Deformation Information 31 

v/vi
EXECUTIVE SUMMARY

The objective of the testing was to establish the tensile strength loss when candidate engine 

mount materials were exposed to a standard flame for 5 and 15 minutes. The exposure time 

dictates the fireproof rating of the material; i.e., a material will be fire resistant if it is capable of

withstanding a 2000°F (±150°F) and 9.8 Btu/ft2

·sec flame for 5 minutes and will be fireproof if it 

can withstand the same flame for 15 minutes while still fulfilling its design purpose. The test

itself was a heat transfer test and not a strength test. Based on temperature measurements, a

comparison was made of the loss of ultimate tensile strength (UTS) of a standardized specimen 

to a reference 4130 steel bar when both are engulfed isothermally to the standard flame. The

UTS data of the materials was obtained from the MIL-Handbook-5H. The comparison metal

bars tested were comprised of the following materials: 15-5 PH steel, titanium 6A1-4V, Inconel 

718, and aluminum 7075. 

The standardized specimens were mounted on a fixture 4 inches in front of the oil burner cone 

and 1 inch above the nozzle horizontal centerline. The 30-inch-long specimens were

instrumented with five thermocouples to measure the temperature within the cross-sectional area

(front, 25% of diameter, 50% of diameter, 75% of diameter, and back). Before the specimens

were exposed to the flame, the flame itself was calibrated using seven thermocouples and four 

calorimeters; the temperature in all the thermocouples was ensured to be within 1850° and 

2150°F and the heat flux on all the calorimeters was set to be above 9.8 Btu/ft2

·sec. The 

specimen’s attachment surface was insulated to minimize heat transfer to the surrounding metal 

surfaces. The flame was calibrated for 2 minutes and the test was conducted for a period of 16

minutes. 

After the test was completed, the MIL-Handbook-5H was employed to determine the effects of 

the measured temperature on the tensile ultimate strength and the tensile yield strength of the 

different metal bars. It was observed that the data in the MIL-Handbook-5H did not account for 

the higher experimental temperatures. However, it was possible to conclude that the 4130 steel, 

which was the reference material, may have lost about 55% of its ultimate strength in the first 5

minutes, but its strength loss at 15 minutes could not be determined because the measured

temperature exceeded the handbook’s published temperature. Comparisons could not be done 

with the 15-5 PH steel and titanium 6A1-4V bars either because of the same reason. The 

titanium bar crept more than the other bars, with the exception of the aluminum bar, creeping 

0.790′′ (maximum recorded) from its original shape. The steel and the Inconel bars did not have 

any significant creeping. Posttest observations revealed that the aluminum 7075 lost all of its 

strength since it melted and split in two pieces after 5 minutes exposure to the standardized fire.

The Inconel 718 bar could only be compared with the handbook during the 5-minute reading. At 

that time, the bar reached 1412.1°F, and according to the handbook chart, the UTS percent loss 

was 50%. No comparison could be made with the 15-minute reading because of the reason 

explained above with regards to the handbook temperature data. During the test, the temperature 

(1644.6°F) exceeded the maximum temperature value (1480°F) plotted in the chart. 

vii/viii
1. INTRODUCTION.

Code of Federal Regulations (CFR) Part 25.865 states “essential flight controls, engine mounts, 

and other flight structures located in designated fire zones or in adjacent areas which would be 

projected to the effects of fire in the fire zone must be constructed of fireproof material or 

shielded so that they are capable of withstanding the effects of fire.” Steel has traditionally been 

accepted as a standard for fireproof material structures. For other materials intended to carry 

loads and resist failure under intense heat, equivalency to steel must be substantiated. Although 

CFR Part 1.1 provides general definitions for the expressions fireproof and fire resistant, they do 

not specify certain parameters associated with testing to positively classify materials into these 

groupings. For the purpose of these tests, the definition of fireproof and fire resistant, as defined 

on Advisory Circular 20-135 [1], was used to examine the tested materials. 

a. Fireproof: The capability of a material to withstand, as well as or better than steel, a 

2000°F flame (±150°F) for 15 minutes minimum while still fulfilling its design purpose. 

The term fireproof, when applied to materials and parts used to confine fires within 

designated fire zones, means that the material or part will perform this function under 

conditions likely to occur in such zones and will withstand a 2000°F flame (150°F) for 15 

minutes minimum.

b. Fire Resistant: When applied to power plant installations such as fluid-carrying lines, 

flammable fluid system components, wiring, air ducts, fittings, and power plant controls, 

fire resistant means the capability of a material or component to perform its intended 

functions under the heat and other conditions likely to occur at the particular location and 

to withstand a 2000°F flame (±150°F) for 5 minutes minimum. 

The primary objective of the testing was to measure the temperature within different solid metal 

cylinders subjected to a standard flame and attempt to determine the impact of the elevated

temperature on the strength of the metals. 

2. TEST SPECIMENS, EQUIPMENT, AND INSTRUMENTATION.

The fire tests were conducted in test cell 1 of building 287 of the Federal Aviation 

Administration (FAA) William J. Hughes Technical Center. The test equipment and 

instrumentation used included a modified oil burner (figure 1), specimen fixture (figure 2), data 

acquisition system, thermocouples, and calorimeters; as described in the following subsections. 

2.1 SPECIMENS.

The specimen materials tested in this program were 4130 steel (reference), 15-5 PH steel, 

titanium 6Al-4V, aluminum 7075, and Inconel 718. The physical dimensions and weight of each 

specimen are tabulated in table 1. The specimens were solid metal bars cut to 30′′ (±1/16) in 

length. Their diameter varied because the specimens were machined to sustain the same ultimate 

tensile load as the reference material (4130 steel), i.e., 88,355 lbf. On this basis, the diameters of 

the comparison bars were determined using the following equation: 

com

ref

com ref Ftu

Ftu

φ = φ × (1)

1
where: 

φ com = Diameter of comparison bar 

φ ref = Diameter of reference bar 

Ftu = Ultimate tensile stress of comparison bar com

Ftu = Ultimate tensile stress of reference bar ref

Three small orifices, 5/64′′ in diameter, were drilled in each specimen for placement of the 

thermocouples used to sense its internal temperature. The depth of the hole depended on the 

percentage of the cross-sectional area being monitored (25%, 50%, and 75% of the diameter). 

2.2 EQUIPMENT.

2.2.1 Modified Oil Burner. 

The oil burner was a modified gun type, Park Model DPL 3400 oil burner (figure 1). A Monarch 

nozzle was installed in the burner to maintain a fuel flow of 2.1 gal/hr, an 80° AR spray pattern, 

an average airflow of 1800 fpm, and a fuel pressure of 94 lb/in2. Jet A fuel was used as the fuel. 

An Internal Turbulator H215 and End Turbulator F124 were installed inside the draft tube and at 

the end of the draft tube. A 12- ±1/8-inch burner cone was installed at the end of the draft tube. 

The cone was made of stainless steel and had a thickness of 0.065 ±0.015 inch. The opening of 

the cone was 6 ±1/4 inches high and 11 ±1/4 inches wide. A vane-type air-sensing anemometer

was used to monitor the flow of the air at the inlet of the oil burner. The inlet was completely 

sealed except for an opening for the air velocity sensor. Flame characteristics were enhanced by 

the optional use of metal tabs installed on the end turbulator. 

2.2.2 Specimen Fixture.

The specimens were mounted, in the main specimen fixture frame shown in figures 2 and 3. 

This fixture was made of 0.125-inch thick welded angled iron, square tubes, and rods. A 

removable secondary structure, which was a frame made of 0.125′′ thick and 1.75′′ wide angled

iron, contained the test specimen and a Kaowool backboard. This frame was clamped to the top 

of the calorimeter frame during the burn test. This frame had two V-notches on the middle of its 

left and right side members, used to place the specimens and align them according to the test

protocols. The main specimen fixture frame also housed the calibration thermocouples and 

calorimeters. The main frame measured 46 inches wide by 64 inches high by 3/4 inch deep. The 

frame holding the Kaowool in place measured 28.25 inches wide by 12 inches high by 1.75 

inches deep. 

2.3 INSTRUMENTATION.

The instrumentation used to collect the test data included a data acquisition system, 

thermocouples, and calorimeters. For posttest measurements, a dial indicator and an indexrotational device were used to measure the deformity (creep) and location on the material. 

2
2.3.1 Data Acquisition System.

The data collection system was comprised of a Computer Boards Inc. PCM-DAS 16S/12 and a 

CIO-EXP16 system connected to a Gateway Solo (Pentium II) laptop computer (figure 4). Each 

data channel was programmed in HP VEE to record once every second. 

2.3.2 Thermocouples. 

The specimen bars were instrumented with thermocouples to determine their internal

temperature gradient. The five thermocouples attached to the specimen bars were placed in front 

of the bar (1/4′′ away from the bar’s surface), embedded inside the bar at 25%, 50%, and 75% of 

its diameter, and on its backside (figure 5). Also, there was a thermocouple pile, with seven 

thermocouples, that was used during the calibration of the flame. The sensing beads of these 

calibration thermocouples were located 4 inches in front of the vertical plane of the oil burner’s 

cone exit and 1 inch above the horizontal centerline of the burner cone [2]. Temperature 

measurements were taken with thermocouples model JSM 1K1EJG24ZZZZZBZ; this 

thermocouple model was Type K, had grounded junction, the wires were 24 AWG, and it had a 

1/16′′ diameter sheath. 

2.3.3 Calorimeter.

Four calorimeters, Vatell model 1000-1A (FAA gage), were used during the calibration of the oil 

burner to determine the total heat flux of the fire. These calorimeters were also located 4 inches

from the vertical plane and offset 1 inch above the horizontal centerline of the burner cone exit 

(figures 6, 7, and 8). The calorimeters’ mounting fixture was interchangeable with the test 

specimen frame. 

2.3.4 Dial Indicator and Index-Rotational Device.

In order to measure any distortion, such as creeping, on the material due to the heat, a dial 

indicator and an index-rotational device were used. A K-D Tools 0- to 1-inch dial indicator, 

1/1000 graduated, was used to measure the deflection on the bars. An L-W index-rotational 

device, from Chuck Company, was used to find the maximum deflection angular location. The 

accuracy of the index-rotational device was 9 degrees per revolution and capable of reading at an

increment of 0.273 degree. 

3. PROCEDURES.

The oil burner was calibrated, on a daily basis, prior to conducting the burn test. After 

calibration, the calorimeter-holding fixture was removed from the test fixture, the thermocouple 

pile was lowered, and the specimen frame was mounted in the calibrated fire zone. After 

mounting the test specimen, the following oil burner procedures test were employed. The 

following sections describe each procedure in detail. 

3.1 CALIBRATION.

Two types of calibration were conducted on the oil burner prior to beginning the tests: 

temperature calibration and total heat flux calibration. The instrumentation setup is shown in 

figure 6. 

3
3.1.1 Temperature Calibration. 

The seven calibration thermocouples were installed, as a thermo pile, in the fire zone to check 

the oil burner’s flame temperature. Each thermocouple was spaced 1 ±1/16 inch apart from each 

other, 4 ±1/8 inches from the vertical plane, and offset 1 ±1/16 inch above the horizontal 

centerline of the burner cone exit (figures 5, 6, and 7). The burner was turned away (rotated 90°

away from the fire zone) from the thermocouples and allowed to preheat for 2 minutes. The 

burner was then directed towards the thermocouples for 90 seconds. During this period, the 

transient temperature was recorded with analog-to-digital converters and displayed in real time. 

The oil burner was adjusted to produce a flame temperature between 1850° and 2150°F, as

measured by each thermocouple. 

3.1.2 Heat Flux Calibration.

The oil burner was also calibrated, to produce a total heat flux at or above 9.8 Btu/ft2·sec. This 

was accomplished by using the four calorimeters described previously. The distance of each of

the four calorimeters was 4 ±1/8 inches from the vertical plane and offset 1 ±1/16 inch above the 

horizontal centerline of the burner cone exit. The burner was rotated away from the calorimeters 

(fire zone) and allowed to preheat for 2 minutes. The burner was then directed towards the 

calorimeters for 90 seconds. The heat flux was recorded with analog-to-digital converters. 

3.2 BURNER TEST.

After calibrating the oil burner, the specimen-mounting frame was attached to the test fixture in a 

manner that exposed the test samples to the same calibration fire intensity. Prior to installing the 

specimen-mounting frame on the test fixture, the specimen bar was instrumented with five

thermocouples and securely fastened to the frame. The thermocouples were installed to measure 

the external (0%) and imbedded internal temperatures of the test specimen at 25%, 50%, 75%, 

and 100% (backside) of the diameter (see figure 5). The thermocouple placed at the 0% mark

was aligned on the outside of the bar and in direct contact with the flame. The thermocouple was

insulated with fiberglass tape except for the last 1/2 inch, which was raised about a 1/4 inch from 

the bar and into the flame. This was performed to ensure the flame produced the correct 

temperature and to minimize conduction from the bar. The test specimen was placed 4 ±1/8 

inches from the vertical plane and offset 1 ±1/16 inch above the horizontal centerline of the 

burner cone exit. Each rod was insulated at the ends to reduce heat transfer from external 

materials and to produce a bar in space scenario. The burner was rotated away from the test 

specimen and allowed to preheat for 2 minutes. The burner was then immediately directed 

towards the test sample, which was heated for 16 minutes (see figure 9). The transient specimen 

bar temperatures were recorded with analog-to-digital converters. 

4. RESULTS.

The results of the burn tests on all five specimens are detailed in the following sections. Table 2 

provides a summary of the test results, figures 10 and 11 are posttest photographs, and figures 12 

through 35 show the time-temperature plots. Figures 36-38 show the tools and technique used to 

measure the creeping effects of the tested materials. After calibrating the oil burner, each type of

metal was tested five times. The average temperature of the thermocouple located at the 50% 

position was used for the comparative analysis (table 3). To be considered fire resistant, the 

residual strength of the test specimen at the 5-minute mark must be equal to or greater than the

4
residual strength of the 4130 steel (reference material) at this time. To be considered fireproof, 

the residual strength of the test specimen at the 15-minute mark must be equal to or greater than 

the residual strength of 4130 steel (reference material) at that time. However, since the measured 

temperatures were generally greater than what was available on the temperature-strength graphs 

in the MIL-Handbook-5H [3], it was difficult to characterize the specimens. Table 4 provides

the material deformation information. 

4.1 4130 STEEL.

After 5 minutes into the burner test, the average temperature of the thermocouple located at the 

50% location was 1131.53°F, corresponding to a residual strength of approximately 45%, as 

viewed in the MIL-Handbook-5H. After 15 minutes, the average temperature of the same

thermocouple was 1513.70°F. Unfortunately, the highest temperature in the MIL-Handbook-5H 

is 1200°F, where the residual strength is 36%. The deflection of each bar was measured after the 

burn test, and the average deflection was 0.172′′ at 127.80° (clockwise) from the thermocouple 

holes. 

4.2 15-5 PH STEEL.

After 5 minutes, the average temperature of the thermocouple located at the 50% location 

reached was 1117.4°F. After 15 minutes, the average temperature of the same thermocouple was

1611.85°F. The highest temperature-strength data in the MIL-Handbook-5H for 15-5 PH steel 

was only 800°F, which corresponds to a residual strength of 79.5%; therefore, a determination 

could not be made of the residual strength at 5 and 15 minutes. The deflection of each bar was 

measured after the burn test, and the average deflection was 0.172′′ at 143.95° (clockwise) from 

the thermocouple holes. Coincidentally, this was the same average deflection as measured with 

the 4130 steel. 

4.3 TITANIUM 6A1-4V. 

After 5 minutes, the average temperature of the thermocouple located at the 50% location was 

1496.48°F. After 15 minutes, the temperature of the same thermocouple was 1646.88°F. The

temperature-strength data in the MIL-Handbook-5H for titanium 6A1-4V extended to only 

1000°F, which corresponds to a residual strength of 51%. Therefore, a comparison between the

two data sources could not be done. The deflection of each bar was measured after the burn test,

and the average deflection was 0.552′′ at 231.71° (clockwise) from the thermocouple holes. 

Titanium experienced a significant amount of creeping when compared to the steels and Inconel. 

The deflection was towards the flame. 

4.4 ALUMINUM 7075.

After 5 minutes, the temperature of the thermocouple located at the 50% location was 1115.6°F. 

Unfortunately, the highest temperature in the MIL-Handbook-5H for aluminum 7075 is 600°F,

where the residual strength is only 11.5%. Shortly after the 5-minute test period, the creep of the 

aluminum 7075 became so drastic that it began melting away; therefore, the test was terminated.

5
4.5 INCONEL 718.

After 5 minutes, the temperature of the thermocouple located at the 50% location was 1412.09°F, 

corresponding to a residual strength of approximately 50%, as viewed in the MIL-Handbook-5H. 

This residual strength would classify Inconel as a fire-resistant material. After 15 minutes, the 

temperature of the same thermocouple was 1644.63°F. Unfortunately, the highest temperature in 

the MIL-Handbook-5H for Inconel 718 is 1500°F, where the residual strength is only 36%. The

deflection was measured after the burn test, and the average deflection was 0.054′′ at 97.98°

(clockwise) from the thermocouple holes. Inconel experienced the least amount of creeping 

deflection compared to the other materials. 

5. REFERENCES.

1. FAA Advisory Circular 20-135, “Powerplant Installation and Propulsion System

Component Fire Protection Test Methods, Standards, and Criteria,” February 1990. 

2. Aircraft Materials Fire Test Handbook, Chapter 7, Oil Burner Test For Seat Cushions, 

7.7 Calibration. 

3. MIL-Handbook-5H Compact Disk, December 1998. 

6
FIGURE 1. OIL BURNER 

30” Solid Metal Bar

Metal Frame

Removable Framed Kaowool (Refractory Ceramic Fiber) 

Board to insulate thermocouples and provide a uniform

and consistent fire impingement surface.

64.00”

12.00”

28.25”

46.00”

Clamps

FIGURE 2. DRAWING OF THE SPECIMEN FIXTURE 

7
FIGURE 3. SPECIMEN FIXTURE 

FIGURE 4. DATA ACQUISITION SYSTEM 

8
Thermocouple Bead

0%

25%

50%

75%

100%

Flame Direction

View A-A

A

A

Use Kaowool (Refractory Ceramic Fiber) Board

to insulate thermocouples and provide uniform

and consistent fire-impingement surface.

TOP VIEW

SIDE VIEW

1/4”

1/4”

FIGURE 5. BAR THERMOCOUPLES INSULATION 

9
(a) Calorimeters Setup. Calibrate the oil burner using four total heat flux

(Gardo l i n gauges) in addition to the seven thermocouples. This will map the heat flux in

firh e-testing zone.

Gardon Gauges (1.0 O” uter Diameter)

11.5”

6.0”

2.0” 1.0”

3.0”

High Density Ceramic Board

(b) Relative position between calorimeters and thermocouples

Gardon Gauge Type K Thermocouple

1.0” 1.0” 1.0” 1.0” 1.0” 1.0”

FIGURE 6. THERMOCOUPLE AND CALORIMETER SETUP 

10
Gardon Gauge

Type K Thermocouple (for Calibration)

Fire Testing Zone (Bar Surface & Thermocouples Placement)

Oil Burner Cone Exit Coverage Area

One-inch below instrumentation centerline

(12.0” x 6.0”)

Kawool Board

FIGURE 7. RELATIVE POSITION BETWEEN CALORIMETERS, CALIBRATION 

THERMOCOUPLES, AND FIRE-TESTING ZONE 

FIGURE 8. CALIBRATION CALORIMETERS 

11
FIGURE 9. FIRE TEST OF 4130 STEEL BAR 

FIGURE 10. 15-5 PH STEEL BAR AFTER TEST 

12
FIGURE 11. ALUMINUM 7075 BAR AFTER TEST 

0

500

1000

1500

2000

2500

0 2 4 6 8 10 12 14 16 18

Time (Min)

Temp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min. Flame Temp

Max. Flame Temp

FIGURE 12. TIME-TEMPERATURE DATA DURING TEST 1 OF 4130 STEEL 

13
0

500

1000

1500

2000

2500

0 2 4 6 8 10 12 14 16 18

Time (Min)

Te

mp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min. Flame Temp

Max Flame Temp

Flame temperature reading was low, but 

pre-test calibration confirms correct 

standard temperature; probable cause 

could be attributed to heat transfer by 

thermocouple touching bar surface. 

FIGURE 13. TIME-TEMPERATURE DATA DURING TEST 2 OF 4130 STEEL 

0

500

1000

1500

2000

2500

0 2 4 6 8 10 12 14 16 18

Time (Min)

Temp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

FIGURE 14. TIME-TEMPERATURE DATA DURING TEST 3 OF 4130 STEEL 

14
0

500

1000

1500

2000

2500

0 2 4 6 8 10 12 14 16 18

Time (Min)

Temp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

FIGURE 15. TIME-TEMPERATURE DATA DURING TEST 4 OF 4130 STEEL 

0

500

1000

1500

2000

2500

0 2 4 6 8 10 12 14 16 18

Time (Min)

Temp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

FIGURE 16. TIME-TEMPERATURE DATA DURING TEST 5 OF 4130 STEEL 

15
0.0

500.0

1000.0

1500.0

2000.0

2500.0

0 2 4 6 8 10 12 14 16 18

Time (Min)

Temp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

FIGURE 17. TIME-TEMPERATURE DATA DURING TEST 1 OF 15-5 PH STEEL 

0

500

1000

1500

2000

2500

0 2 4 6 8 10 12 14 16 18

Time (Min)

Te

mp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

FIGURE 18. TIME-TEMPERATURE DATA DURING TEST 2 OF 15-5 PH STEEL 

16
0

500

1000

1500

2000

2500

0 2 4 6 8 10 12 14 16 18

Time (Min)

Te

mp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

FIGURE 19. TIME-TEMPERATURE DATA DURING TEST 3 OF 15-5 PH STEEL 

0

500

1000

1500

2000

2500

0 2 4 6 8 10 12 14 16 18

Time (Min)

Te

mp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

FIGURE 20. TIME-TEMPERATURE DATA DURING TEST 4 OF 15-5 PH STEEL 

17
0

500

1000

1500

2000

2500

0 2 4 6 8 10 12 14 16 18

Time (Min)

Te

mp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

FIGURE 21. TIME-TEMPERATURE DATA DURING TEST 5 OF 15-5 PH STEEL 

0

500

1000

1500

2000

2500

0 2 4 6 8 10 12 14 16 18

Time (Min)

Te

mp (degF)

Temp at 0% (degF)

Temp at 75% (degF)

Temp at 50% (degF)

Temp at 25% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

FIGURE 22. TIME-TEMPERATURE DATA DURING TEST 1 OF TITANIUM 6A1-4V 

18
0

500

1000

1500

2000

2500

0 2 4 6 8 10 12 14 16 18

Time (Min)

Te

mp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

FIGURE 23. TIME-TEMPERATURE DATA DURING TEST 2 OF TITANIUM 6A1-4V 

0

500

1000

1500

2000

2500

0 2 4 6 8 10 12 14 16 18

Time (Min)

Temp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

FIGURE 24. TIME-TEMPERATURE DATA DURING TEST 3 OF TITANIUM 6A1-4V 

19
0

500

1000

1500

2000

2500

0 2 4 6 8 10 12 14 16 18

Time (Min)

Te

mp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame

Max Flame

Fire breached insulation of the 100% thermocouple

FIGURE 25. TIME-TEMPERATURE DATA DURING TEST 4 OF TITANIUM 6A1-4V 

0

500

1000

1500

2000

2500

0 2 4 6 8 10 12 14 16 18

Time (Min)

Te

mp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Falme Temp

Fire breached insulation of the 100% thermocouple

FIGURE 26. TIME-TEMPERATURE DATA DURING TEST 5 OF TITANIUM 6A1-4V 

20
0

500

1000

1500

2000

2500

0 1 2 345 6 7 8 9 10

Time (Min)

Temp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

FIGURE 27. TIME-TEMPERATURE DATA DURING TEST 1 OF ALUMINUM 7075 

0

500

1000

1500

2000

2500

0 1 2 345 6 7 8 9 10

Time (Min)

Temp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

FIGURE 28. TIME-TEMPERATURE DATA DURING TEST 2 OF ALUMINUM 7075 

21
0

500

1000

1500

2000

2500

0 1 2 345 6 7 8 9 10

Time (Min)

Temp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min flame Temp

Max Flame Temp

FIGURE 29. TIME-TEMPERATURE DATA DURING TEST 3 OF ALUMINUM 7075 

0

500

1000

1500

2000

2500

0 1 2 3 4 5 6 7 8 9 10

Time (Min)

Temp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

FIGURE 30. TIME-TEMPERATURE DATA DURING TEST 4 OF ALUMINUM 7075 

22
0

500

1000

1500

2000

2500

0 1 2 345 6 7 8 9 10

Time (Min)

Temp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

FIGURE 31. TIME-TEMPERATURE DATA DURING TEST 5 OF ALUMINUM 7075 

0.0

500.0

1000.0

1500.0

2000.0

2500.0

0 2 4 6 8 10 12 14 16 18

Time (Min)

Temp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

FIGURE 32. TIME-TEMPERATURE DATA DURING TEST 1 OF INCONEL 718 

23
0

500

1000

1500

2000

2500

02468 10 12 14 16 18

Time (Min)

Temp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

Fire breached insulation of the 100% thermocouple

FIGURE 33. TIME-TEMPERATURE DATA DURING TEST 2 OF INCONEL 718 

0

500

1000

1500

2000

2500

02468 10 12 14 16 18

Time (Min)

Temp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

Fire breached insulation of the 100% thermocouple

FIGURE 34. TIME-TEMPERATURE DATA DURING TEST 3 OF INCONEL 718 

24
0.0

500.0

1000.0

1500.0

2000.0

2500.0

0 2 4 6 8 10 12 14 16 18

Time (Min)

Temp (degF)

Temp at 0% (degF)

Temp at 25% (degF)

Temp at 50% (degF)

Temp at 75% (degF)

Temp at 100% (degF)

Min Flame Temp

Max Flame Temp

FIGURE 35. TIME-TEMPERATURE DATA DURING TEST 4 OF INCONEL 718 

FIGURE 36. TEST FIXTURE DURING THE DETERMINATION OF THE 

SPECIMEN MAXIMUM DEFLECTION 

25
Laser Pointer

Metal Specimen Bar

Index Rotational Device

(9 Degrees per 1 revolution)

FIGURE 37. TEST FIXTURE DURING THE DETERMINATION OF THE SPECIMEN 

MAXIMUM DEFLECTION ANGULAR LOCATION 

26
d

d = Bar Deflection

Solid Metal Bar Specimen

a

Oil Burner

Flames

(180 Angle)

Angle from thermocouple holes

to maximum deflection point (creep)

0

90

180

270

Thermocouple Holes

(at 0 Angle)

(a) Illustration of Specimen Maximum Deflection

(b) Illustration of the Specimen Maximum Deflection Angular Location

FIGURE 38. SPECIMEN MAXIMUM DEFLECTION LOCATION 

27
TABLE 1. TEST SPECIMEN DESCRIPTION 

Material Bar No. Actual Length (in.) Calculated Diameter (in.) Actual Diameter (in.) Actual Weight (lbs.)

Steel 4130

1 30.1 1.250 1.241 10.5

2 30.1 1.250 1.245 10.5

3 30.1 1.250 1.242 10.5

4 30.1 1.250 1.241 10.5

5 30.1 1.250 1.240 10.5

Steel 15-5PH

1 30.0 0.953 0.950 10.3

2 30.0 0.953 0.955 10.3

3 30.0 0.953 0.953 10.3

4 30.0 0.953 0.952 10.3

5 30.0 0.953 0.940 10.3

Aluminum 7075

1 30.0 1.286 1.275 3.9

2 30.0 1.286 1.282 3.9

3 30.0 1.286 1.280 3.9

4 30.0 1.286 1.280 3.9

5 30.0 1.286 1.278 3.9

Titanium 6AI-4V

1 30.0 0.938 0.931 3.2

2 30.0 0.938 0.931 3.2

3 30.0 0.938 0.935 3.2

4 30.0 0.938 0.935 3.2

5 30.0 0.938 0.935 3.2

Inconel 718

1 30.0 0.972 0.861 5.9

2 30.0 0.972 0.861 5.9

3 30.0 0.972 0.97 5.9

4 30.0 0.972 0.861 5.9

5 30.0 0.972 0.862 5.9

28
Test Test Material Temp (degF) AT 5 Minutes Temp (degF) AT 15 Minutes Comments

Number ID At 0% D At 25% D At 50% D At 75% D At 100% D At 0% D At 25% D At 50% D At 75% D At 100% D

1 052003T3 4130 Steel 2031.4 1319.6 1310.1 1305.9 1244.0 2049.8 1612.8 1609.5 1608.5 1555.12 052103T1 4130 Steel 1878.0 1131.5 1094.5 1077.8 1038.5 1856.8 1562.9 1533.6 1516.4 1468.03 052103T2 4130 Steel 1979.4 1273.5 1253.8 1231.9 1195.5 1955.1 1596.8 1577.3 1556.6 1513.44 052203T2 4130 Steel 1848.4 1087.0 1029.4 1009.8 972.6 1892.3 1478.8 1430.9 1409.4 1376.65 052903T1 4130 Steel 1789.1 1016.4 969.9 948.4 906.0 1792.9 1462.9 1417.0 1403.0 1365.0 Thermocouple at 0% reading low due to contact with bar.6 060903T1 15-5PH Steel 1861.9 1126.4 1094.3 1068.6 1040.5 1876.0 1627.3 1602.0 1570.4 1499.07 060903T2 15-5PH Steel 1926.8 1153.1 1128.4 1064.3 1097.3 1906.5 1641.4 1620.5 1560.4 1555.18 061003T3 15-5PH Steel 1906.4 1114.8 1122.1 1125.1 1123.1 1900.4 1615.4 1612.1 1603.4 1543.59 061003T4 15-5PH Steel 1925.9 1132.5 1096.4 1062.3 967.4 1898.0 1639.6 1613.3 1579.4 1472.5

10 061003T5 15-5PH Steel 1905.3 1188.5 1146.0 1111.9 1041.6 1901.6 1633.4 1611.4 1583.9 1478.011 061203T1 Titanium 6AI-4V 2003.4 1447.4 1439.9 1421.9 1360.4 2011.6 1644.9 1626.1 1608.6 1535.812 061203T2 Titanium 6AI-4V 2003.6 1491.6 1447.6 1434.9 1365.6 1984.5 1707.3 1679.6 1658.8 1581.913 061203T3 Titanium 6AI-4V 1978.5 1597.0 1557.9 1539.4 1470.5 1950.8 1679.3 1651.8 1635.3 1614.414 061303T5 Titanium 6AI-4V 1999.0 1515.3 1519.5 1514.1 1512.0 1979.1 1637.4 1629.6 1628.5 1605.515 061603T4 Titanium 6AI-4V 1937.9 1524.1 1517.5 1508.0 1484.1 1924.4 1653.0 1647.3 1638.6 1666.016 080803T1 Aluminum 7075 1863.8 1099.1 1090.6 1085.6 1086.8 N/A N/A N/A N/A N/A Aluminum bar started to melt after 5 minutes17 080803T2 Aluminum 7075 1884.6 1121.3 1121.1 541.1 1136.6 N/A N/A N/A N/A N/A Aluminum bar started to melt after 5 minutes18 080803T3 Aluminum 7075 1967.8 1115.4 1105.1 1096.6 1207.8 N/A N/A N/A N/A N/A Aluminum bar started to melt after 5 minutes19 080803T4 Aluminum 7075 1965.3 1125.4 1123.5 1118.4 1173.3 N/A N/A N/A N/A N/A Aluminum bar started to melt after 5 minutes20 080803T5 Aluminum 7075 1804.4 1138.6 1137.4 1326.1 1360.9 N/A N/A N/A N/A N/A Aluminum bar started to melt after 5 minutes21 061703T1 Inconel 718 1995.3 1243.3 1232.8 1227.5 1204.6 1991.4 1599.5 1604.9 1599.3 1513.822 071603T2 Inconel 718 2008.8 1516.9 1526.5 1536.5 1579.8 1997.4 1657.5 1668.4 1682.9 1659.923 072103T3 Inconel 718 1999.1 1256.0 1321.9 1336.6 1365.0 1988.3 1576.9 1639.1 1659.1 1558.524 072103T4 Inconel 718 2043.0 1537.9 1567.3 1599.8 1493.6 2050.4 1646.3 1666.1 1692.5 1604.525 072903T5 Inconel 718 N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A Test Aborted - Fire destroyed thermocouple connections

D = Diameter

TABLE 2. SUMMARY OF RESULTS

29
TABLE 3. COMPARISON BETWEEN TEST DATAAND MIL-HANDBOOK-5H

Material Average Temperature MIL-Handbook-5H Average Temperature MIL-Handbook-5H Comments

of 50% Diameter at

5 Minutes Data - UTS Percent Loss (%) of 50% Diameter at 15 Minutes Data - UTS Percent Loss (%)

4130 Steel 1131.5 55 1513.7 Not able to compare

MIL-Handbook-5H (Figure 2.3.1.1.1)only shows data up to 1200degF,which results in a 64% loss of UTS(1/2-hour exposure to flame)

15-5 PH Steel 1117.4 Not able to compare 1611.9 Not able to compare

MIL-Handbook-5H (Figure 2.6.6.1.1)only shows data up to 800degF,which results in a 20% loss of UTS(1/2-hour exposure to flame)

Titanium 6AI-4V 1496.5 Not able to compare 1646.9 Not able to compare

MIL-Handbook-5H (Figure 5.4.1.1.1)only shows data up to 1000degF,which results in a 49% loss of UTS(1/2-hour exposure to flame)

Aluminum 7075 1115.6 100 N/A N/A

MIL-Handbook-5H (Figure 3.7.4.1.1.c) only shows data up to600degF, which results in a 89%loss of UTS (1/2-hour exposure to flame). Bar melted after 5 minutes ofexposure.

Inconel 718 1412.1 50 1644.6 Not able to compare

MIL-Handbook-5H (Figure 6.3.5.1.1)only shows data up to 1480degF,which results in a 68% loss of UTS(1/2-hour exposure to flame).

30
TABLE 4. MATERIAL DEFORMATION INFORMATION 

Maximum Angular Location of

Material Deformation Type Deflection (in)* Maximum Deflection (deg) Comments

4130 Steel Bar 1 Crept 0.128 102 Angle measured clockwise from thermocouple holes on the bar.

4130 Steel Bar 2 Crept 0.132 131.46 Angle measured clockwise from thermocouple holes on the bar.

4130 Steel Bar 3 Crept 0.100 148.9 Angle measured clockwise from thermocouple holes on the bar.

4130 Steel Bar 4 Crept 0.358 133.06 Angle measured clockwise from thermocouple holes on the bar.

4130 Steel Bar 5 Crept 0.140 123.55 Angle measured clockwise from thermocouple holes on the bar.

Average 4130 Steel 0.172 127.794 Angle measured clockwise from thermocouple holes on the bar.

15-5PH Steel Bar 1 Crept 0.187 129.54 Angle measured clockwise from thermocouple holes on the bar.

15-5PH Steel Bar 2 Crept 0.177 138.28 Angle measured clockwise from thermocouple holes on the bar.

15-5PH Steel Bar 3 Crept 0.200 168.83 Angle measured clockwise from thermocouple holes on the bar.

15-5PH Steel Bar 4 Crept 0.128 144 Angle measured clockwise from thermocouple holes on the bar.

15-5PH Steel Bar 5 Crept 0.166 139.09 Angle measured clockwise from thermocouple holes on the bar.

Average 15-5PH Steel 0.172 143.948

Titanium 6AI-4V Bar 1 Crept 0.485 238.91 Angle measured clockwise from thermocouple holes on the bar.

Titanium 6AI-4V Bar 2 Crept 0.360 227.18 Angle measured clockwise from thermocouple holes on the bar.

Titanium 6AI-4V Bar 3 Crept 0.748 225 Angle measured clockwise from thermocouple holes on the bar.

Titanium 6AI-4V Bar 4 Crept 0.376 234 Angle measured clockwise from thermocouple holes on the bar.

Titanium 6AI-4V Bar 5 Crept 0.790 233.46 Angle measured clockwise from thermocouple holes on the bar.

Average Titanium 0.552 231.710

Aluminum 7075 Bar 1 Melted N/A N/A N/A

Aluminum 7075 Bar 2 Melted N/A N/A N/A

Aluminum 7075 Bar 3 Melted N/A N/A N/A

Aluminum 7075 Bar 4 Melted N/A N/A N/A

Aluminum 7075 Bar 5 Melted N/A N/A N/A

Inconel 718 Bar 1 Crept 0.020 45 Angle measured clockwise from thermocouple holes on the bar.

Inconel 718 Bar 2 Crept 0.033 29.46 Angle measured clockwise from thermocouple holes on the bar.

Inconel 718 Bar 3 Crept 0.098 177.28 Angle measured clockwise from thermocouple holes on the bar.

Inconel 718 Bar 4 Crept 0.064 140.18 Angle measured clockwise from thermocouple holes on the bar.

Inconel 718 Bar 5 - - - -

Average Inconel 718 0.054 97.980 Angle measured clockwise from thermocouple holes on the bar.

*Note: Deflection was measured from a horizontal line at the table to the maximum bend point on the bottom of the bar.

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